DC Field | Value | Language |
---|---|---|
dc.contributor.author | Won, Dae-Yeon | ko |
dc.contributor.author | Tahk, Min-Jea | ko |
dc.contributor.author | Kim, Yoon-Hwan | ko |
dc.date.accessioned | 2013-03-08T18:06:39Z | - |
dc.date.available | 2013-03-08T18:06:39Z | - |
dc.date.created | 2012-02-06 | - |
dc.date.created | 2012-02-06 | - |
dc.date.issued | 2010-06 | - |
dc.identifier.citation | INTERNATIONAL JOURNAL OF AERONAUTICAL AND SPACE SCIENCES , v.11, no.2, pp.131 - 135 | - |
dc.identifier.issn | 2093-274X | - |
dc.identifier.uri | http://hdl.handle.net/10203/93847 | - |
dc.description.abstract | We report on the design of a three-axis missile autopilot using multi-objective control synthesis via linear matrix inequality techniques. This autopilot design guarantees H₂/H<SUB>∞</SUB> performance criteria for a set of finite linear models. These models are linearized at different aerodynamic roll angle conditions over the flight envelope to capture uncertainties that occur in the high-angle-of-attack regime. Simulation results are presented for different aerodynamic roll angle variations and show that the performance of the controller is very satisfactory. | - |
dc.language | English | - |
dc.publisher | 한국항공우주학회 | - |
dc.title | Three-Axis Autopilot Design for a High Angle-Of-Attack Missile Using Mixed H-2/H-infinity Control | - |
dc.type | Article | - |
dc.type.rims | ART | - |
dc.citation.volume | 11 | - |
dc.citation.issue | 2 | - |
dc.citation.beginningpage | 131 | - |
dc.citation.endingpage | 135 | - |
dc.citation.publicationname | INTERNATIONAL JOURNAL OF AERONAUTICAL AND SPACE SCIENCES | - |
dc.contributor.localauthor | Tahk, Min-Jea | - |
dc.contributor.nonIdAuthor | Won, Dae-Yeon | - |
dc.contributor.nonIdAuthor | Kim, Yoon-Hwan | - |
Items in DSpace are protected by copyright, with all rights reserved, unless otherwise indicated.